CN115610643B - Unmanned aerial vehicle undercarriage that takes precautions against earthquakes - Google Patents
Unmanned aerial vehicle undercarriage that takes precautions against earthquakes Download PDFInfo
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- CN115610643B CN115610643B CN202211388776.6A CN202211388776A CN115610643B CN 115610643 B CN115610643 B CN 115610643B CN 202211388776 A CN202211388776 A CN 202211388776A CN 115610643 B CN115610643 B CN 115610643B
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- unmanned aerial
- aerial vehicle
- plate
- fixedly connected
- connecting plate
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/04—Arrangement or disposition on aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/58—Arrangements or adaptations of shock-absorbers or springs
- B64C25/62—Spring shock-absorbers; Springs
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Abstract
The invention discloses an unmanned aerial vehicle shockproof landing gear, wherein a shock absorption landing leg is rotationally connected below a fixing frame, an installation box is fixedly connected in the middle of the lower part of the fixing frame, a shockproof mechanism is movably connected inside the installation box, the top of the shockproof mechanism penetrates through the fixing frame and is fixedly connected with a connecting plate, and an installation plate is elastically connected above the connecting plate; the shockproof mechanism comprises a pressing component and a speed reducing component. According to the invention, when the unmanned aerial vehicle falls, the downward movement speed of the connecting plate can be slowed down, and the push rod can not push the spiral rotating plate to rotate any more due to the reduction of the downward pressure of the unmanned aerial vehicle, so that the unmanned aerial vehicle can fall; and ejector rod on the spacing rack can stretch into the circular slot this moment, and is spacing to the whole locking that carries out of undercarriage, and the cooperation of each structure of undercarriage can realize multistage buffering, improves the stability when unmanned aerial vehicle main part descends.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle shockproof landing gear.
Background
The unmanned aerial vehicle is an aircraft which does not need any manual driving operation of a driver to carry out boarding, can automatically complete all flight processes under the monitoring of electronic equipment, and the appearance of the unmanned aerial vehicle makes the research of various countries on the aircraft enter a brand-new era. The unmanned aerial vehicle has the advantages of strong survivability, high flexibility, good maneuverability and very convenient use. The miniature rotor unmanned aerial vehicle is a product of micro-electromechanical system integration, and becomes a key point of many laboratory researches at home and abroad by virtue of the advantages of capability of taking off and landing vertically, free hovering, flexible control, strong capability of adapting to various environments and the like. The system research of the miniature rotor unmanned aerial vehicle mainly aims at a ground control system and an airborne measurement and control communication system, and the ground control system can monitor and command and control the flight attitude of the unmanned aerial vehicle; the airborne measurement and control communication system is mainly used for collecting data of an inertial sensor, an ultrasonic distance meter and the like in the flight state of the unmanned aerial vehicle and transmitting the data to the ground control system. Be equipped with the undercarriage on the rotor unmanned aerial vehicle for take off or the in-process of landing to rotor unmanned aerial vehicle supports, and rotor unmanned aerial vehicle can produce great impact force at the in-process of landing, and current rotor unmanned aerial vehicle undercarriage generally adopts spring structure to cushion this impact force to protect rotor unmanned aerial vehicle, however, the mode of spring buffering can make unmanned aerial vehicle rock from top to bottom when the landing, and even bounce repeatedly after striking with ground falls, leads to stability when unmanned aerial vehicle falls not high. Therefore, there is a need for an unmanned aerial vehicle anti-vibration landing gear.
Disclosure of Invention
The invention aims to provide an unmanned aerial vehicle shockproof landing gear so as to solve the problems in the prior art.
In order to achieve the above object, the present invention provides the following solutions: the invention provides an unmanned aerial vehicle shockproof landing gear which comprises a fixed frame, wherein a shock absorption supporting leg is rotationally connected below the fixed frame, an installation box is fixedly connected to the middle part below the fixed frame, a shockproof mechanism is movably connected to the inside of the installation box, the top of the shockproof mechanism penetrates through the fixed frame and is fixedly connected with a connecting plate, and an installation plate is elastically connected above the connecting plate; the vibration prevention mechanism comprises a pressing component and a speed reduction component, the pressing component comprises a pressing rack, the pressing rack is meshed with a gear, the gear is rotationally connected with the mounting box, the gear is meshed with a limiting rack, and the limiting rack is detachably connected with the connecting plate; the speed reducing assembly comprises a spiral rotating plate, the spiral rotating plate is connected with the inside of the installation box in a rotating mode, a push rod is connected to the spiral rotating plate in a sliding mode, and one end, away from the spiral rotating plate, of the push rod is fixedly connected with the bottom of the connecting plate.
Preferably, the shock attenuation landing leg is provided with four, every shock attenuation landing leg includes branch and fixed plate, the one end of branch with the corner of mount rotates to be connected, the fixed plate rotates to be connected with the telescopic link, the telescopic link is kept away from the one end of fixed plate with the pole body of branch rotates to be connected.
Preferably, the connecting plate is provided with a plurality of grooves, and springs are fixedly connected inside the grooves; the mounting plate is fixedly provided with a plurality of sliding rods towards the connecting plate, and the sliding rods are respectively in one-to-one correspondence with the grooves; the sliding rod is in sliding connection with the groove, a baffle is fixedly arranged on the rod body of the sliding rod, one end of the spring is fixedly connected with the bottom of the groove, and the other end of the spring is fixedly connected with the baffle; and one side of the groove is provided with a clamping assembly which is detachably connected with the baffle.
Preferably, the circular groove is formed in the connecting plate, the circular groove is close to the groove, a through hole is formed in the side wall between the circular groove and the groove, the clamping assembly is located inside the through hole, the clamping assembly comprises a clamping block which is in sliding connection with the inner wall of the through hole, a tension spring is fixedly connected between the top surface of the clamping block and the inner wall of the through hole, the length of the clamping block is larger than that of the through hole, and the end face of the clamping block located at one end of the circular groove is an inclined surface which is inclined downwards.
Preferably, teeth are arranged on two opposite side surfaces of the downward-pressing rack, sliding strips are fixedly connected to the middle parts of the other two side surfaces of the downward-pressing rack, and the two sliding strips are in sliding connection with the fixing frame; the top of the downward-pressing rack is fixedly connected with the connecting plate.
Preferably, two limiting racks are arranged, the two limiting racks are symmetrically arranged relative to the pressing rack, and one side, away from the pressing rack, of each limiting rack is in sliding connection with the inner wall of the mounting box; the top of the limiting rack is fixedly connected with a push rod, the push rod is in sliding connection with the circular groove, and the push rod is detachably connected with the clamping block.
Preferably, the bottom of the fixing frame is fixedly connected with a cross rod, and the cross rod penetrates through two opposite side walls of the mounting box and is fixedly connected with the mounting box; the gear is rotationally connected with the cross rod.
Preferably, two push rods are provided, each push rod is L-shaped, one end of each push rod, which is close to the spiral rotating plate, is rotationally connected with a ball, and the ball is rotationally connected with the spiral rotating plate; the spiral rotating plate comprises a rotating shaft and a spiral plate, the rotating shaft is vertically arranged inside the installation box, the rotating shaft is rotationally connected with the inside of the installation box, and the rotating shaft is fixedly connected with the spiral plate.
Preferably, the support legs are arranged at the bottom of the installation box, and rubber blocks are fixedly arranged between the support legs and the installation box.
Preferably, a plurality of connecting rods are arranged between the connecting plates and the fixing frame, one end of each connecting rod is connected with the connecting plates in a rotating way, and the other ends of the connecting rods are connected with the top surface of the fixing frame in a rotating way.
The invention discloses the following technical effects: according to the invention, the pressing component and the speed reducing component are arranged below the fixing frame, the pressing component and the speed reducing component are not in elastic structures, when the unmanned aerial vehicle falls down, the connecting plate moves downwards to press the pressing rack, the pressing rack drives the limiting rack to move upwards, at the moment, the push rod is matched with the spiral rotating plate, the downward moving speed of the connecting plate can be slowed down, and the push rod can not push the spiral rotating plate to rotate any more due to the reduction of the downward pressure of the unmanned aerial vehicle, so that the unmanned aerial vehicle falls down; and ejector rod on the spacing rack can stretch into the circular slot this moment, and is spacing to the whole locking that carries out of undercarriage, and the cooperation of each structure of undercarriage can realize multistage buffering, improves the stability when unmanned aerial vehicle main part descends.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions of the prior art, the drawings that are needed in the embodiments will be briefly described below, it being obvious that the drawings in the following description are only some embodiments of the present invention, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic view of the internal structure of a shock-resistant landing gear of the present invention;
FIG. 2 is an enlarged view of a portion of FIG. 1A;
FIG. 3 is a side view of the anti-rattle landing gear of the present invention;
FIG. 4 is an enlarged view of a portion of B in FIG. 3;
fig. 5 is a schematic structural diagram of a clamping assembly according to the present invention.
Wherein: 1. a mounting plate; 2. a connecting plate; 3. a push rod; 4. a clamping block; 5. a telescopic rod; 6. a support rod; 7. a mounting box; 8. a support leg; 9. a rubber block; 10. a limit rack; 11. a gear; 12. a slide bar; 13. pressing down the rack; 14. a fixing plate; 15. a fixing frame; 16. a cross bar; 17. a circular groove; 18. a connecting rod; 19. a push rod; 20. a spiral plate; 21. a rotating shaft; 22. a ball; 23. a spring; 24. a through hole; 25. a tension spring; 26. a baffle; 27. a slide bar; 28. a groove.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
In order that the above-recited objects, features and advantages of the present invention will become more readily apparent, a more particular description of the invention will be rendered by reference to the appended drawings and appended detailed description.
Referring to fig. 1-5, the invention provides an unmanned aerial vehicle anti-vibration landing gear, which comprises a fixed frame 15, wherein a vibration-damping landing leg is rotationally connected below the fixed frame 15, an installation box 7 is fixedly connected to the middle part below the fixed frame 15, an anti-vibration mechanism is movably connected to the inside of the installation box 7, the top of the anti-vibration mechanism penetrates through the fixed frame 15 and is fixedly connected with a connecting plate 2, and a mounting plate 1 is elastically connected above the connecting plate 2; the shockproof mechanism comprises a pressing component and a deceleration component, the pressing component comprises a pressing rack 13, the pressing rack 13 is meshed with a gear 11, the gear 11 is rotationally connected with the mounting box 7, the gear 11 is meshed with a limiting rack 10, and the limiting rack 10 is detachably connected with the connecting plate 2; the speed reducing assembly comprises a spiral rotating plate, the spiral rotating plate is in rotary connection with the inside of the installation box 7, a push rod 19 is connected to the spiral rotating plate in a sliding mode, and one end, away from the spiral rotating plate, of the push rod 19 is fixedly connected with the bottom of the connecting plate 2. According to the invention, the pressing component and the speed reducing component are arranged below the fixing frame 15, the pressing component and the speed reducing component are not in elastic structures, when the unmanned aerial vehicle falls down, the connecting plate 2 moves down to press the pressing rack 13, the pressing rack 13 drives the limiting rack 10 to move up, at the moment, the push rod 19 is matched with the spiral rotating plate, the downward moving speed of the connecting plate 2 can be slowed down, and the push rod 19 can not push the spiral rotating plate to rotate any more due to the reduction of the downward pressure of the unmanned aerial vehicle, so that the unmanned aerial vehicle can fall down; and ejector rod 3 on spacing rack 10 can stretch into in the circular slot 17 this moment, and is spacing to the landing gear whole locking, and the cooperation of each structure of landing gear can realize multistage buffering, improves the stability when unmanned aerial vehicle main part descends.
The four shock-absorbing support legs are arranged, each shock-absorbing support leg comprises a support rod 6 and a fixed plate 14, one end of the support rod 6 is rotationally connected with a corner of a fixing frame 15, the fixed plate 14 is rotationally connected with a telescopic rod 5, and one end, far away from the fixed plate 14, of the telescopic rod 5 is rotationally connected with a rod body of the support rod 6; the damping support leg can rotate outwards when being subjected to downward pressure, and the telescopic rod 5 plays a role in buffering at the moment, so that the phenomenon that the landing gear is inclined due to overlarge deflection angle of the damping support leg is avoided; the telescopic rod 5 is a hydraulic rod.
A plurality of grooves 28 are formed in the connecting plate 2, and springs 23 are fixedly connected inside the grooves 28; the mounting plate 1 is fixedly provided with a plurality of sliding rods 27 towards the connecting plate 2, and the sliding rods 27 and the grooves 28 are respectively in one-to-one correspondence; the slide bar 27 is in sliding connection with the groove 28, a baffle plate 26 is fixedly arranged on the bar body of the slide bar 27, one end of the spring 23 is fixedly connected with the bottom of the groove 28, and the other end of the spring 23 is fixedly connected with the baffle plate 26; one side of the groove 28 is provided with a clamping assembly which is detachably connected with the baffle 26. The mounting plate 1 is used for being fixedly mounted with the unmanned aerial vehicle, so that the unmanned aerial vehicle and the landing gear are integrally formed into an organic whole; the limiting ring is arranged at the opening of the groove 28 on the connecting plate 2 and fixedly connected with the opening of the groove 28, and is used for limiting the baffle 26 and preventing the sliding rod 27 from slipping off the groove 28.
The connecting plate 2 is provided with a round groove 17, the round groove 17 is arranged close to the groove 28, a through hole 24 is formed in the side wall between the round groove 17 and the groove 28, the clamping assembly is located inside the through hole 24 and comprises a clamping block 4 which is slidably connected with the inner wall of the through hole 24, a tension spring 25 is fixedly connected between the top surface of the clamping block 4 and the inner wall of the through hole 24, the length of the clamping block 4 is greater than that of the through hole 24, and the end face of the clamping block 4 located at one end of the round groove 17 is an inclined surface which inclines downwards. There is the clearance between connecting plate 2 and mounting panel 1 for realize buffering when unmanned aerial vehicle descends, in order to prevent spring 23 bounce, fixture block 4 when baffle 26 moves down, ejector pin 3 enters into circular slot 17, and ejector pin 3 can promote fixture block 4 translation, realizes blockking to baffle 26, forms the locking.
Teeth are respectively arranged on two opposite side surfaces of the downward-pressing rack 13, sliding strips 12 are fixedly connected to the middle parts of the other two side surfaces of the downward-pressing rack 13, and the two sliding strips 12 are in sliding connection with a fixing frame 15; the top of the downward-pressing rack 13 is fixedly connected with the connecting plate 2.
The two limiting racks 10 are symmetrically arranged about the pressing rack 13, and one side of each limiting rack 10 away from the pressing rack 13 is in sliding connection with the inner wall of the mounting box 7; the top of the limiting rack 10 is fixedly connected with a push rod 3, the push rod 3 is in sliding connection with the circular groove 17, and the push rod 3 is detachably connected with the clamping block 4. The ejector rod 3 enters the circular groove 17 to push the clamping block 4, and at the moment, the limiting rack 10 and the pressing rack 13 are mutually matched, so that a 'multi-rod supporting' fixing mode can be realized, and the whole landing gear becomes more stable.
The bottom of the fixing frame 15 is fixedly connected with a cross rod 16, and the cross rod 16 penetrates through two opposite side walls of the mounting box 7 and is fixedly connected with the mounting box 7; the gear 11 is rotatably connected with the cross bar 16.
The two push rods 19 are arranged, each push rod 19 is L-shaped, one end of each push rod 19 close to the spiral rotating plate is rotationally connected with a ball 22, and the ball 22 is rotationally connected with the spiral rotating plate; the spiral rotating plate comprises a rotating shaft 21 and a spiral plate 20, the rotating shaft 21 is vertically arranged inside the installation box 7, the rotating shaft 21 is rotationally connected with the inside of the installation box 7, and the rotating shaft 21 is fixedly connected with the spiral plate 20. The box body is arranged at the position where the bottom of the rotating shaft 21 is connected with the mounting box 7, a spring is arranged in the box body and is connected with the rotating shaft 21, when the rotating shaft 21 rotates, the spring can be continuously tightened, and the rotating shaft 21 can rotate only with larger force at the moment, so that the push rod 19 is a gradual deceleration process when the spiral plate 20 is pressed downwards, and the stability of the unmanned aerial vehicle can be ensured at all times; when the ejector rod 3 of the limiting rack 10 enters the circular groove 17, the rotating shaft 21 does not move any more, and the spring is in a tightened state; when the unmanned aerial vehicle takes off, under the effect of clockwork spring, the part in each position of undercarriage can get back to initial position voluntarily.
The stabilizer blade 8 is installed to mounting box 7 bottom, fixedly is provided with rubber piece 9 between stabilizer blade 8 and the mounting box 7.
A plurality of connecting rods 18 are arranged between the connecting plate 2 and the fixing frame 15, one end of each connecting rod 18 is connected with the rotating connection of the connecting plate 2, and the other end of each connecting rod 18 is connected with the top surface of the fixing frame 15 in a rotating manner.
The working process comprises the following steps: when the unmanned aerial vehicle is in actual use, the unmanned aerial vehicle is arranged on the mounting plate 1, when the unmanned aerial vehicle wants to land, the damping support legs firstly touch the ground, and when the unmanned aerial vehicle continues to land, the damping support legs can be extruded to the outer side, and at the moment, the telescopic rod 5 can play a role in buffering the damping support legs; meanwhile, when the unmanned aerial vehicle is pressed downwards, the pressing rack 13 moves downwards, the pressing rack 13 drives the gear 11 to rotate, the gear 11 drives the limiting rack 10 to move upwards, when the ejector rod 3 on the limiting rack 10 moves upwards into the circular groove 17, the ejector rod 3 pushes the clamping block 4 to move towards one side of the groove 28, and at the moment, the sliding rod 27 in the groove 28 is bottomed under the extrusion of the unmanned aerial vehicle, so that the baffle 26 is positioned below the clamping block 4, and the clamping block 4 can limit the baffle 26; meanwhile, when the connecting plate 2 moves downwards, the push rod 19 can squeeze the spiral rotating plate, and as a spring is connected below the rotating shaft 21 of the spiral rotating plate, the spiral rotating plate can play a role in decelerating the push rod 19; when the ejector rod 3 is positioned inside the circular groove 17, the unmanned aerial vehicle landing is completed.
In the description of the present invention, it should be understood that the terms "longitudinal," "transverse," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like indicate or are based on the orientation or positional relationship shown in the drawings, merely to facilitate description of the present invention, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus should not be construed as limiting the present invention.
The above embodiments are only illustrative of the preferred embodiments of the present invention and are not intended to limit the scope of the present invention, and various modifications and improvements made by those skilled in the art to the technical solutions of the present invention should fall within the protection scope defined by the claims of the present invention without departing from the design spirit of the present invention.
Claims (7)
1. An unmanned aerial vehicle undercarriage that takes precautions against earthquakes, its characterized in that: the shock-absorbing support comprises a fixing frame (15), shock-absorbing support legs are rotationally connected below the fixing frame (15), an installation box (7) is fixedly connected to the middle of the lower portion of the fixing frame (15), a shock-absorbing mechanism is movably connected to the inside of the installation box (7), the top of the shock-absorbing mechanism penetrates through the fixing frame (15) and is fixedly connected with a connecting plate (2), and a mounting plate (1) is elastically connected above the connecting plate (2); the vibration prevention mechanism comprises a pressing component and a speed reduction component, the pressing component comprises a pressing rack (13), the pressing rack (13) is meshed with a gear (11), the gear (11) is rotationally connected with the mounting box (7), the gear (11) is meshed with a limiting rack (10), and the limiting rack (10) is detachably connected with the connecting plate (2); the speed reducing assembly comprises a spiral rotating plate, the spiral rotating plate is in rotational connection with the inside of the installation box (7), a push rod (19) is connected to the spiral rotating plate in a sliding manner, and one end, far away from the spiral rotating plate, of the push rod (19) is fixedly connected with the bottom of the connecting plate (2);
a plurality of grooves (28) are formed in the connecting plate (2), and springs (23) are fixedly connected inside the grooves (28); a plurality of sliding rods (27) are fixedly arranged on the mounting plate (1) towards the connecting plate (2), and the sliding rods (27) and the grooves (28) are respectively in one-to-one correspondence; the sliding rod (27) is in sliding connection with the groove (28), a baffle plate (26) is fixedly arranged on the rod body of the sliding rod (27), one end of the spring (23) is fixedly connected with the bottom of the groove (28), and the other end of the spring (23) is fixedly connected with the baffle plate (26); a clamping assembly is arranged on one side of the groove (28), and the clamping assembly is detachably connected with the baffle (26);
the connecting plate (2) is provided with a round groove (17), the round groove (17) is close to the groove (28) and is arranged, a through hole (24) is formed in the side wall between the round groove (17) and the groove (28), the clamping assembly is positioned in the through hole (24), the clamping assembly comprises a clamping block (4) which is in sliding connection with the inner wall of the through hole (24), a tension spring (25) is fixedly connected between the top surface of the clamping block (4) and the inner wall of the through hole (24), the length of the clamping block (4) is larger than that of the through hole (24), and the end surface of the clamping block (4) positioned at one end of the round groove (17) is a downward inclined surface;
the two limiting racks (10) are symmetrically arranged about the pressing racks (13), and one side, away from the pressing racks (13), of each limiting rack (10) is in sliding connection with the inner wall of the installation box (7); the top of the limiting rack (10) is fixedly connected with a push rod (3), the push rod (3) is in sliding connection with the circular groove (17), and the push rod (3) is detachably connected with the clamping block (4).
2. The unmanned aerial vehicle anti-vibration landing gear of claim 1, wherein: the shock attenuation landing leg is provided with four, every shock attenuation landing leg includes branch (6) and fixed plate (14), the one end of branch (6) with the corner of mount (15) rotates to be connected, fixed plate (14) rotate and are connected with telescopic link (5), telescopic link (5) are kept away from the one end of fixed plate (14) with the shaft of branch (6) rotates to be connected.
3. The unmanned aerial vehicle anti-vibration landing gear of claim 1, wherein: teeth are formed on two opposite side surfaces of the downward-pressing rack (13), sliding strips (12) are fixedly connected to the middle parts of the other two side surfaces of the downward-pressing rack (13), and the two sliding strips (12) are in sliding connection with the fixing frame (15); the top of the downward-pressing rack (13) is fixedly connected with the connecting plate (2).
4. The unmanned aerial vehicle anti-vibration landing gear of claim 1, wherein: a cross rod (16) is fixedly connected to the bottom of the fixing frame (15), and the cross rod (16) penetrates through two opposite side walls of the mounting box (7) and is fixedly connected with the mounting box (7); the gear (11) is rotationally connected with the cross bar (16).
5. The unmanned aerial vehicle anti-vibration landing gear of claim 1, wherein: two push rods (19) are arranged, each push rod (19) is L-shaped, one end of each push rod (19) close to the spiral rotating plate is rotatably connected with a ball (22), and the ball (22) is rotatably connected with the spiral rotating plate; the spiral rotating plate comprises a rotating shaft (21) and a spiral plate (20), wherein the rotating shaft (21) is vertically arranged inside the installation box (7), the rotating shaft (21) is rotationally connected with the inside of the installation box (7), and the rotating shaft (21) is fixedly connected with the spiral plate (20).
6. The unmanned aerial vehicle anti-vibration landing gear of claim 1, wherein: the bottom of the installation box (7) is provided with supporting legs (8), and rubber blocks (9) are fixedly arranged between the supporting legs (8) and the installation box (7).
7. The unmanned aerial vehicle anti-vibration landing gear of claim 1, wherein: a plurality of connecting rods (18) are arranged between the connecting plates (2) and the fixing frames (15), one end of each connecting rod (18) is connected with the connecting plates (2) in a rotating mode, and the other ends of the connecting rods (18) are connected with the top surfaces of the fixing frames (15) in a rotating mode.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211388776.6A CN115610643B (en) | 2022-11-08 | 2022-11-08 | Unmanned aerial vehicle undercarriage that takes precautions against earthquakes |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211388776.6A CN115610643B (en) | 2022-11-08 | 2022-11-08 | Unmanned aerial vehicle undercarriage that takes precautions against earthquakes |
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| Publication Number | Publication Date |
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| CN115610643A CN115610643A (en) | 2023-01-17 |
| CN115610643B true CN115610643B (en) | 2023-07-04 |
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Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105059532B (en) * | 2015-07-16 | 2017-11-28 | 湖南省金峰机械科技有限公司 | A kind of unmanned plane undercarriage |
| CN110877716B (en) * | 2019-12-06 | 2022-04-22 | 湖南浩天翼航空技术有限公司 | Elastic support undercarriage based on rack transmission for fixed wing type unmanned aerial vehicle |
| CN211893627U (en) * | 2020-01-17 | 2020-11-10 | 丁武轩 | Plant protection unmanned aerial vehicle's integral type undercarriage |
| CN211996120U (en) * | 2020-04-08 | 2020-11-24 | 杭州明启勘测规划设计有限公司 | Four-wing unmanned aerial vehicle buffering undercarriage |
| CN214776527U (en) * | 2020-10-22 | 2021-11-19 | 陕西锐锋信息技术有限公司 | Unmanned aerial vehicle with descending shock-absorbing function |
| CN214112855U (en) * | 2020-12-31 | 2021-09-03 | 深圳市鸿辉塑胶制品有限公司 | Utilize unmanned aerial vehicle descending seismic isolation device of gear drive principle |
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